Integrity evaluation of aging structures is extremely important to ensure economic and safe operation of the flight vehicle. A two step analytical approach has been developed to estimate the residual strength/life of pressurized fuselage stiffened shell panels with widespread fatigue cracking. Global FEA, to obtain the load flow pattern through the damaged panel, is followed by the Schwartz-Neumann Alternating Method to determine the relevant crack tip parameters that govern the growth of cracks and onset of failure. An Elastic-Plastic Alternativing Method has been developed and applied to evaluate the residual strength of flat panels with multiple cracks. The computational methodologies presented herein are marked improvements to the present state-of-the-art, and are extremely efficient, both from engineering manpower as well as computational costs point of view.
Structural integrity of panels with multisite fatigue damage
Bauliche Unversehrtheit von Platten mit Mehrfachermüdungsschäden
1994
10 Seiten, 11 Bilder, 4 Tabellen, 12 Quellen
Conference paper
English
Structural Integrity of Fuselage Panels with Multisite Damage
Online Contents | 1995
|Simulation of structural integrity predictions for panels with multiple site damage
Tema Archive | 2000
|Multisite Damage Assessment Tool
Springer Verlag | 2015
|